【无人机】用于送货服务的无人机（Matlab实现）

最新推荐文章于 2025-11-24 17:52:36 发布

原创最新推荐文章于 2025-11-24 17:52:36 发布 · 498 阅读

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#无人机

💥💥💞💞欢迎来到本博客❤️❤️💥💥

🏆博主优势：🌞🌞🌞博客内容尽量做到思维缜密，逻辑清晰，为了方便读者。

⛳️座右铭：行百里者，半于九十。

📋📋📋本文目录如下：🎁🎁🎁

💥1 概述

用于送货服务的无人机是一种自动化飞行系统，旨在实现货物的安全、高效地从一个地点送达到另一个地点，而无需人员直接操作。送货服务的无人机旨在解决货物运输中的最后一英里问题，可以应用于快递、物流、紧急医疗援助等领域。其任务包括从配送中心或者指定地点获取货物，飞行至目的地，将货物准确地投递给接收者。随着技术的不断发展和应用场景的拓展，送货服务的无人机将进一步完善和普及。未来可能出现更多针对特定场景和需求的定制化解决方案，以及与其他智能系统的深度集成，实现更高效、更智能的货物运输服务。

📚2 运行结果

主函数部分代码：

clc;
%SETUP
W=3.52;      %All-up weight of UAV in lbf
N_motors=4;  %Number of motors
n=0.85;      %Average efficiency of motors
RPM=8000;    %Estimated setup RPM

%BATTERY
V=11;        %Selected motor voltage in volts
C=5200;      %Battery cell capacity in mAh

%PROPELLER
D = 10;          %Propeller diameter in inches
Pitch=4.7;       %Propeller pitch in inches
A=0.25*3.14*D^2; %Propeller sweep area in square inches
Aft=A*0.0069;    %Propeller sweep area in square feet

%FULL THROTLE
i=1;
for P_in=0.01:0.01:0.1  
    PL= (P_in*n)/Aft;               %Power loading equation
    TL = 8.6859*power(PL,-0.3107);  %Thrust loading equation
    Lift = TL*(P_in*n);             %Lift per Motor
    LiftTotal = Lift *N_motors;     %Total lift of the UAV
    PinWatt=P_in*745.7;             %Power input to motor in Watts
    disp(PinWatt);
    disp(LiftTotal);
    x(i)=PinWatt;
    y(i)=LiftTotal;
        if LiftTotal > 2*W
            break
        end
    i=i+1;
end
plot(x,y,'Marker','o') ;
xlswrite('1.xls',x);
xlswrite('2.xls',y);

            
Imotor = PinWatt/V;         %Current of motor
Itot = Imotor*N_motors;     %Total UAV current
PoutWatt =PinWatt*n ;       %Power relation involving motor efficiency 
KVreq = RPM /V;             %Required KV of motor
NomKVreq = KVreq/n;         %Nominal KV (labeled) of motorwhich accounts for efficiency
ESCreq = Imotor*1.2;        %Required ESC current for motor

%HOVER
j=1;
for PH_in=0.01:0.01:0.1
    PL_H = (PH_in*n)/Aft;              %Power loading equation for hover
    TL_H = 8.6859*power(PL_H,-0.3107); %Thrust loading equation for hover
    Lift_H = TL_H *(PH_in*n);          %Lift per motor at hover
    Lift_HTotal = Lift_H*N_motors;     %Total lift of the UAV at hover
    PH_inWatt = PH_in*745.7;           %Power input to motor at hover in Watts
    disp(PH_inWatt);
    disp(Lift_HTotal);
        if Lift_HTotal>W
            break
        end
    j=j+1;
end
I_Hmotor = PH_inWatt/V;           %Current of motor at hover
I_Htot = I_Hmotor * N_motors;     %Total hover UAV current
PH_outWatt = PH_inWatt*n;         %Power relation involving motor efficiency